A controller for a drive system, the drive system comprising a permanent magnet machine, wherein the controller is configured to receive a short circuit signal indicating that a short circuit failure has been detected in the drive system and in response to receiving the short circuit signal, control the permanent magnet machine into a braking mode, wherein in the braking mode, energy is drawn from the permanent magnet machine in order to decelerate the permanent magnet machine.
H02P 21/22 - Current control, e.g. using a current control loop
H02K 15/03 - Processes or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of stator or rotor bodies having permanent magnets
An apparatus may include a generator, an electrical converter, and multiple ice protection heaters. The generator may be configured to generate alternating current (AC) along AC feeders. The electrical converter may be configured to convert the AC from the generator to direct current (DC). The ice protection heaters may include at least one ice protection heater connected to each of the AC feeders prior to the electrical converter. The ice protection heaters may be configured to generate heat at surfaces susceptible to icing using the AC from the generator.
An apparatus for driving an accessory includes an electric starter/generator (ESG) including a rotor shaft. The apparatus also includes a permanent magnet motor/generator (PMMG) associated with the rotor shaft. The apparatus also includes a gear coupled to a rotor of the PMMG for rotating in a first mode and for rotating in a second mode responsive to rotation of the rotor shaft, wherein rotation of the gear drives the accessory. The application of a current to a stator of the PMMG is configured to cause rotation of the rotor and the gear coupled to the rotor in the first mode when a rotation speed of the rotor is faster than a rotation speed of the rotor shaft. When the rotation speed of the rotor shaft equals the rotation speed of the rotor, the rotor is configured to engage the rotor shaft to rotate concurrently therewith in the second mode.
H02K 7/00 - Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
H02K 7/116 - Structural association with clutches, brakes, gears, pulleys or mechanical starters with gears
4.
METHOD FOR IMPLEMENTING A FULL INPUT SOURCE POWER INPUT CONTROL FUNCTION ON MULTIPLE POWER INPUTS TO A SINGLE LLC CONVERTER IN A DISTRIBUTION SYSTEM
A power SS circuit includes N power input circuits, an output node configured to connect to an input node of voltage-fed power converter, and a control interface that receives control signals for controlling operational/non-operational states switches within the power input circuits. The power input circuits include N input nodes connected to N power sources, respectively. Each respective power input circuit includes: a SS capacitor including a first terminal connected to ground; an SS switch including a first terminal as a respective input node among the input nodes and configured to connect a second terminal of the SS capacitor to the respective input node in the operational state; and a voltage-fed converter switch including a first terminal connected to a second terminal of the SS switch and configured to connect the second terminal of the SS capacitor to the output node of power SS circuit in the operational state.
H02M 3/335 - Conversion of DC power input into DC power output with intermediate conversion into AC by static converters using discharge tubes with control electrode or semiconductor devices with control electrode to produce the intermediate AC using devices of a triode or a transistor type requiring continuous application of a control signal using semiconductor devices only
A journal bearing shaft is provided and includes a single monolithic body. The single monolithic body includes a tie rod, an end cap integrally connected to and extending radially outwardly from an end of the tie rod and defining openings, a journal bearing interface portion integrally connected to and extending aft from a distal edge of the end cap and a heat exchanger integrally connected to and extending aft from an aft edge of the journal bearing interface portion and including an exterior body and heat exchange fins extending radially between the exterior body and the tie rod.
A conversion coating system, a bifunctional conversion coating, a coated product including the bifunctional conversion coating, and a method of manufacture thereof. The conversion coating system includes a bifunctional polymeric additive composition and a conversion coating composition, wherein the conversion coating composition includes a dye compound. The conversion coating composition and the bifunctional polymeric additive composition are configured to be provided separately, combined, or a combination thereof.
A first electrical machine is configured to act as an electrical motor in a first mode and an electrical generator in a second mode. Each first electrical machine is associated with a high-pressure spool of a turbine engine. A first controller is configured to control a load level of the first electrical machine responsive to a first load level control signal. A second electrical machine is configured to act as an electrical motor in the first mode and as an electrical generator in the second mode. The second electrical machine is associated with a low-pressure spool of the turbine engine. A second controller is configured to control a load level of the second electrical machine responsive to a second load level control signal. A third controller is configured to generate the first load level control signal and the second load level control signal responsive to temperatures of the first electrical machine, the first controller, the second electrical machine, and the second controller.
A fuel system includes a system inlet and a system outlet. The fuel system also includes a metering valve with a metering valve inlet fluidically connected to the system inlet, and a metering valve outlet fluidically connected to the metering valve inlet. A pressure regulating valve includes an inlet fluidically connected to the metering valve outlet, and an outlet fluidically connected to the system outlet. A spool of the pressure regulating valve is configured to fluidically open and close the inlet to the outlet. The pressure regulating valve also includes a control chamber on a control side of the spool. A pilot valve includes a return port fluidically connected to the system outlet, and a supply port fluidically connected to a line fluidically connecting the metering valve outlet to the inlet of the pressure regulating valve. The pilot valve also includes a signal port fluidically connected to the control chamber.
F02M 37/00 - Apparatus or systems for feeding liquid fuel from storage containers to carburettors or fuel-injection apparatusArrangements for purifying liquid fuel specially adapted for, or arranged on, internal-combustion engines
A fluid system includes a reference pressure source, a first valve, and a second valve. The first valve includes a housing with a first damping port fluidically connected to the reference pressure source and a second damping port fluidically connected to the reference pressure source. The first valve also includes a spool moveable within the housing. The spool includes a damping window formed on the spool. The damping window fluidically connects the first damping port to the second damping port. The second valve is fluidically connected to at least one of the first damping port and the second damping port.
A method includes receiving, by an electronic device via a data bus, status information associated with a set of circuit breakers (CBs) of the aircraft. The status information includes an identifier and current state of each among the set. The method includes obtaining a database including on aircraft test procedure (OATP) CB tables in a second data format and including the CB identifier and an expected state of each CB among the set. The method includes translating the status information from a first data format to the second data format, thereby generating a translated current state of each CB among the set. The method includes, for each respective CB among the set, determining whether the translated current state and the expected state conflict and in response to identifying a conflict between the expected state and the translated current state, generating a command to change the current state.
H04L 67/12 - Protocols specially adapted for proprietary or special-purpose networking environments, e.g. medical networks, sensor networks, networks in vehicles or remote metering networks
H04L 67/125 - Protocols specially adapted for proprietary or special-purpose networking environments, e.g. medical networks, sensor networks, networks in vehicles or remote metering networks involving control of end-device applications over a network
11.
DETECTING POWER LINE DISCONTINUITIES TO PROTECT AGAINST ARC FAULTS
An apparatus may include a solid-state power controller (SSPCs), a pulse generator, a feedback detector, and a microcontroller. The SSPC may be configured to output power from a power source to an aircraft electrical load. The pulse generator may be configured to generate a pulse through the SSPC. The pulse feedback detector may be configured to detect a response pulse from the generated pulse reflected from the aircraft electrical load, wherein the pulse feedback detector may be operably coupled to a power output of the SSPC. The microcontroller may be configured to trip the SSPC when the response pulse detected by a corresponding pulse feedback detector operably coupled to the SSPC is determined to be abnormal.
G01R 31/00 - Arrangements for testing electric propertiesArrangements for locating electric faultsArrangements for electrical testing characterised by what is being tested not provided for elsewhere
An apparatus includes a generator including an input shaft, a jet engine including a low pressure spool, and a multi-speed transmission mechanically coupling the low pressure spool to the input shaft. The apparatus further includes a transmission controller configured to disengage an electrical load from the generator, while the electrical load is disengaged from the generator, perform a shifting operation of the multi-speed transmission, and after performing the shifting operation, reengage the electrical load to the generator.
F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries
F16H 61/682 - Control functions within change-speed- or reversing-gearings for conveying rotary motion specially adapted for stepped gearings with interruption of drive
A motor includes a housing. The motor includes a stator with a plurality of slots disposed axially along an axis of rotation of a rotor, the stator having a first end and a second end, wherein the first end and second end are separated along the axis of rotation of the rotor. The motor includes stator windings disposed on the plurality of slots, the stator windings comprising a core set of windings, a first set of end turns proximate to the first end, and a second set of end turns proximate to the second end. The motor includes a cooling sleeve surrounding the stator windings, the cooling sleeve having a first opening proximate to the first end of the stator, and a second opening proximate to the second end of the stator and a thermally conductive dissipation cap thermally connected to the cooling sleeve.
A crank gear includes a shaft extending along a centerline. A first bearing, a second bearing, and a gear are mounted to the shaft. An interface at the first end of the shaft for rotating the shaft and the gear about the centerline. The crank gear is reversibly insertable through a port of a gearbox to engage a gear. The gear is rotationally coupled to a rotor of a gas turbine engine.
An axial variable displacement piston pump includes a drive shaft disposed on an axis, a piston barrel comprising a plurality of pistons disposed about the drive shaft, and a swash plate disposed about the drive shaft. Each of the piston barrel and the swash plate are rotationally coupled to the drive shaft such that the drive shaft is configured to simultaneously drive rotation of each of the piston barrel and the swash plate.
Apparatus and associated methods relate to using an electro-hydraulic solenoid valve to provide regulation of fluid displacement of a variable-displacement hydraulic pump. A mechanical control mechanism is configured to control displacement of hydraulic fluid pumped from a hydraulic input port to a hydraulic output port. The electro-hydraulic solenoid valve regulates fluid conductivity between a hydraulic output port of the variable-displacement hydraulic pump and a hydraulic control cylinder, which operates a hydraulic control piston coupled to the mechanical control mechanism controlling fluid displacement. An electronic control unit is configured to generate and transmit an electrical control signal to the electro-hydraulic solenoid valve in response to a metric of the variable-displacement hydraulic pump as measured by a transducer. The electronic control unit generates the electrical control signal so as to control the metric measured to within a predetermined control band about a target value.
F04B 49/00 - Control of, or safety measures for, machines, pumps, or pumping installations, not otherwise provided for in, or of interest apart from, groups
An air turbine starter (ATS) assembly for an aircraft has an ATS mounted to an accessory drive gearbox. The ATS includes an ATS output shaft is configured to pass from the ATS into the accessory drive gearbox. The accessory drive gearbox includes an overrunning clutch assembly configured to rotationally connect the ATS output shaft to an accessory gearbox shaft when the overrunning clutch engages the ATS output shaft such that the overrunning clutch assembly transmits rotational energy from the ATS output shaft to an accessory gearbox shaft. The overrunning clutch assembly is configured to permit the accessory gearbox shaft to rotate independent of the ATS output shaft when the overrunning shaft is disengaged from the ATS output shaft. The overrunning clutch assembly is configured to be removeable from the accessory drive gearbox as a removeable clutch cartridge.
A radio frequency (RF) integrated gate driver includes a galvanically-isolated (GI) waveguide and an RF rectifier. The GI waveguide is configured to receive an RF signal from an RF source and to generate a rectifier input signal based on the RF signal. The RF rectifier is configured to receive the rectifier input signal from the GI waveguide and to generate, based on the rectifier input signal, a rectifier output signal to drive a gate of a power switch device.
H02M 1/08 - Circuits specially adapted for the generation of control voltages for semiconductor devices incorporated in static converters
H02M 1/44 - Circuits or arrangements for compensating for electromagnetic interference in converters or inverters
H03K 17/16 - Modifications for eliminating interference voltages or currents
H03K 17/0812 - Modifications for protecting switching circuit against overcurrent or overvoltage without feedback from the output circuit to the control circuit by measures taken in the control circuit
19.
ELECTRIC POWER GENERATORS WITH INTEGRATED HIGH-SPEED AND HIGH-POWER PERMANENT MAGNET GENERATORS
An apparatus includes a main generator including a first rotor shaft configured to operate at a first speed and generate a first electrical output responsive to rotation of the first rotor shaft. The apparatus also includes a secondary generator including a second rotor shaft located coaxially with the first rotor shaft and configured to generate a second electrical output responsive to rotation of the second rotor shaft. The apparatus further includes a planetary gear set that interconnects the first rotor shaft with the second rotor shaft and that enables the first rotor shaft to drive the second rotor shaft at a second speed higher than the first speed. In addition, the apparatus includes a housing that surrounds the main generator, the secondary generator, and the planetary gear set.
An electrical system for protecting an aircraft from electrical faults includes an AC-DC switching converter and a controller for controlling the AC-DC switching converter. The AC-DC switching converter includes a set of AC phase lines for electrical coupling to an electrical machine of the aircraft, a plurality of converter switches, and a positive DC line and a negative DC line for electrical coupling to a DC bus of the aircraft. The controller is configured, in response to receiving a signal indicative of an electrical fault in wiring or equipment electrically coupled to the AC-DC switching converter, to close two or more of the plurality of converter switches so as to electrically couple two or more of the AC phase lines to a common one of the DC lines for a period of time spanning a plurality of revolutions of the electrical machine.
H02H 7/22 - Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions for distribution gear, e.g. bus-bar systemsEmergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions for switching devices
A leakage detection system for an isolated earth system of an aircraft includes a common bus, a plurality of switches, and at least one connector. The at least one connector is arranged to connect at least one of the plurality of switches to at least one component of the isolated earth system. At least one of the plurality of switches is arranged to control the draw of power from the common bus. The leakage detection system also includes a switch driver arranged to control the plurality of switches between a plurality of configurations. The leakage detection system is arranged to determine a location of a leakage using a measurement of the insulation monitoring device.
B64F 5/60 - Testing or inspecting aircraft components or systems
G01R 31/00 - Arrangements for testing electric propertiesArrangements for locating electric faultsArrangements for electrical testing characterised by what is being tested not provided for elsewhere
An air conditioning system of a vehicle includes an air cycle system configured to receive a medium and provide a conditioned form of the medium to one or more loads. A vapor compression cycle has a closed loop configuration and a liquid loop through which a first liquid circulates is thermally and fluidly connected to the vapor compression cycle. The liquid loop is also thermally and fluidly connected to the air cycle system at an air cycle system heat exchanger. The liquid loop includes a heat exchanger arranged upstream from the air cycle system heat exchanger relative to a flow of the first liquid. The first liquid is arranged in a heat transfer relationship with a second liquid at the heat exchanger. The first liquid is cooled by the second liquid and/or the medium to achieve a desired temperature at a location downstream from the air cycle system heat exchanger.
Apparatus and associated methods relate to using a Pulse-Width Modulated (PWM) electro-hydraulic solenoid valve to provide regulation of fluid displacement pumped by a variable-displacement hydraulic pump. The PWM electro-hydraulic solenoid valve regulates fluid conductivity between a hydraulic output port and a hydraulic control port of the variable-displacement hydraulic pump. Such regulation of fluid conductivity therebetween controls fluid displacement through the variable-displacement hydraulic pump. An electronic control unit is configured to generate and transmit a PWM electrical control signal to the PWM electro-hydraulic solenoid valve in response to a metric of the variable-displacement hydraulic pump as measured by a transducer. The electronic control unit generates the PWM electrical control signal so as to control the metric measured to within a predetermined control band about a target value.
F04B 49/12 - Control of, or safety measures for, machines, pumps, or pumping installations, not otherwise provided for in, or of interest apart from, groups by varying the length of stroke of the working members
24.
CONDITIONALLY REGULATED HYBRID ELECTRIC HVDC ARCHITECTURE
A method includes determining an operating mode of a hybrid electric propulsion system. The hybrid electric propulsion system includes a conditionally regulated high voltage direct current (HVDC) architecture. The conditionally regulated HVDC architecture includes a first switchable circuit formed between an HVDC bus, an HVDC electrical source, and a bi-directional direct current to direct current (DC-DC) converter configured to regulate electrical power flowing between the HVDC bus and the HVDC electrical source. The conditionally regulated HVDC architecture also includes a second switchable circuit formed between the HVDC bus and the HVDC electrical source. The method also includes configuring the conditionally regulated HVDC architecture based on the determined operating mode.
Apparatus and associated methods relate to a hydraulic pressure-relief valve having a path of fluid flow during a pressure-relief event that does not engage a valve control mechanism. Such separation of the path of fluid flow and the valve control mechanism prevents pressure droop caused by momentum exchanges between flowing fluid and the valve control mechanism. Such separation is realized by forming a branched hydraulic channel within a piston portion of a nozzle. A longitudinal branch of the branched hydraulic channel provides fluid to a cylindrical cavity of a slidable sleeve that is slidably coupled to the piston portion of the nozzle. A radial branch of the branched hydraulic channel is selectively blocked by a slidable sleeve, which functions as the control mechanism. In response to pressure of hydraulic fluid in the cylindrical cavity, the slidable sleeve longitudinally slides away from the nozzle thereby exposing the pressure-relief port.
F16K 17/04 - Safety valvesEqualising valves opening on surplus pressure on one sideSafety valvesEqualising valves closing on insufficient pressure on one side spring-loaded
26.
ENVIRONMENTAL CONTROL SYSTEM WITH INTEGRATED VAPOR COMPRESSION SYSTEM AND AIR CYCLE MACHINE
An environmental control system (ECS) of an aircraft, having: a case; a vaper compression system (VCS) having a compressor and a driven shaft coupled to the compressor, wherein the compressor and the driven shaft are sealed within the case; and an air cycle machine (ACM) including a first turbine and a drive shaft coupled to the first turbine and which are outside the case, wherein the drive shaft and the driven shaft are coupled to each other via a coupling.
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
27.
ENVIRONMENTAL CONTROL SYSTEM OF AN AIRCRAFT CONFIGURED WITH A HERMETICALLY SEALED TURB-COMPRESSOR COUPLED TO A SHAFT VIA AN AXIAL FLUX MOTOR
An environmental control system of an aircraft, having: a cooling circuit including: a sealed housing; a turbo-compressor hermetically sealed within the housing, wherein the turbo-compressor includes: a compressor fluidly coupled to the circuit; a turbine fluidly coupled to the circuit downstream of the compressor; a shaft operably coupling the compressor and the turbine; an axial flux motor generator coupled to the turbo-compressor; and an exterior shaft, located exterior to the housing and operably coupled to the motor generator, wherein the motor generator includes: a first rotor within the housing that is coupled to the compressor; and a second rotor that is outside the housing and coupled to the exterior shaft, and wherein the stator includes windings, the first rotor has a first number of magnets and the second rotor have a second number of magnets that is different than the first number of magnets.
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
28.
CROSS-FLOW THREE-WAY AMMONIA-TO-AIR HEAT EXCHANGER FOR AIR CONDITIONING APPLICATIONS ON AN AIRCRAFT
An aircraft system for pre-heating ammonia that flows toward an ammonia fuel cell, the system having: an ammonia-to-air heat exchanger, having: a first section through which RAM air flows, a second section through which the ammonia flows and a third section between the first and second sections which includes a solvent, wherein heat energy is transferred from the RAM air to the ammonia via the solvent; and an ammonia sensor that provides an alert when ammonia is detected in the solvent.
An apparatus includes a transient voltage suppression (TVS) device configured to be coupled in parallel with a burden resistor. The apparatus also includes a switch configured to couple the TVS device across the burden resistor. The apparatus further includes a comparator configured to detect a peak output voltage provided by a circuit, determine whether the peak output voltage meets or exceeds a threshold, and control the switch based on whether the peak output voltage meets or exceeds the threshold.
H02H 3/28 - Emergency protective circuit arrangements for automatic disconnection directly responsive to an undesired change from normal electric working condition, with or without subsequent reconnection responsive to difference between voltages or between currentsEmergency protective circuit arrangements for automatic disconnection directly responsive to an undesired change from normal electric working condition, with or without subsequent reconnection responsive to phase angle between voltages or between currents involving comparison of the voltage or current values at two spaced portions of a single system, e.g. at opposite ends of one line, at input and output of apparatus
H02H 9/00 - Emergency protective circuit arrangements for limiting excess current or voltage without disconnection
H02H 9/04 - Emergency protective circuit arrangements for limiting excess current or voltage without disconnection responsive to excess voltage
30.
Powered turbo-expander combining centrifugal compressor and an axial flow turbine
An environmental control system (ECS) of an aircraft, having a heat exchanger; a compressor that receives a first airflow from a first air source, compresses the first airflow, and directs the first airflow to the heat exchanger; an axial flow turbine that receives a second airflow from a second air source, extracts energy from the second airflow, and directs the second airflow to the heat exchanger, wherein the heat exchanger directs the first airflow to a cabin of the aircraft and directs the second airflow overboard; and a shaft connected between the turbine and the compressor.
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
F04D 17/10 - Centrifugal pumps for compressing or evacuating
F04D 19/00 - Axial-flow pumps specially adapted for elastic fluids
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
Pressure relief valves include a valve housing having an inlet end wall and an inner cavity defined within the valve housing. An inlet opening defining a valve seat is formed within the inlet end wall. A valve ball is configured to sealingly engage with the valve seat to seal the inlet opening. A ball carrier is arranged to retain the valve ball between the ball carrier and the inlet end wall. A biasing element is configured to bias the ball carrier toward the inlet end wall. An end stop element is configured to threadedly engage with an interior surface of the valve housing and the biasing element is biased against a stop surface of the end stop element. A locking nut is configured to threadedly engage with an end of the end stop element and secure the end stop element to the valve housing.
F16K 17/04 - Safety valvesEqualising valves opening on surplus pressure on one sideSafety valvesEqualising valves closing on insufficient pressure on one side spring-loaded
F16K 27/02 - Construction of housingsUse of materials therefor of lift valves
An air turbine starter for a gas turbine engine includes a clutch with an input component and an output component. The input component includes a base and turbine blades connected to the base and extending radially outward from the base relative to a center axis of the air turbine starter. An overrun mechanism connects the base of the input component to the output component and is configured to transfer rotational energy from the input component to the output component and prevent the output component from transferring rotational energy to the input component. A first end of a transfer shaft is connected to the output component of the clutch. A gear system is connected to a second end of the transfer shaft. An output shaft is mechanically connected to the transfer shaft by the gear system.
An environmental control system of an aircraft, having: a cooling circuit including: a sealed housing; a turbo-compressor sealed within the housing, wherein the turbo-compressor includes: a compressor fluidly coupled to the circuit; a turbine fluidly coupled to the circuit downstream of the compressor, wherein the turbine is a flash turbine; a shaft operably coupling the compressor and the turbine; and a motor generator operably coupled to the turbo-compressor and disposed within the housing.
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
A lattice coalescer is provided and includes an architected lattice having a cylindrical shape with an upstream end and a downstream end. The architected lattice includes a solid outer body and an interior body disposed within the solid outer body and substantially filled in three dimensions with tessellated unit cells. The tessellated unit cells are arranged with respect to one another in a cell map such that a fog-laden airflow moving through the architected lattice from the upstream end to the downstream end exhibits a pressure drop of 2 psi or less and formation of water droplets of 10-40 microns.
Oxygen generation systems for use in low-gravity environments include a cell stack having an anode and a cathode. An anode-side phase separator and a cathode-side phase separator are each fluidly coupled to outlets of the cell stack. The anode-side phase separator separates a mixture into liquid water and gaseous oxygen and the cathode-side phase separates a mixture int liquid water and gaseous hydrogen. A ducting system is configured to house the cell stack and the cathode-side phase separator, a hydrogen sensor is arranged at an outlet of the ducting system, and a controller is configured to stop oxygen generation at the cell stack when a concentration of hydrogen is detected at or above a threshold level at the hydrogen sensor at the outlet of the ducting system.
A slot liner for an electric machine is arranged to be located and removably retained in a slot of a machine to secure a winding in the slot. The slot liner includes a flexible electrically non-conductive material defining a body having a first surface to be located against a wall of the slot and an opposing surface configured to receive a winding therearound. The slot liner also includes a phase separator arm extending adjacent but spaced from the opposing surface, where the opposing surface and the phase separator arm define a space therebetween to accommodate a winding when mounted onto the slot liner. In use, the separator arm extends along the slot to separate a winding mounted on the slot liner from another winding secured in the slot by a slot liner on an adjacent tooth.
H02K 3/34 - Windings characterised by the shape, form or construction of the insulation between conductors or between conductor and core, e.g. slot insulation
H02K 3/12 - Windings characterised by the conductor shape, form or construction, e.g. with bar conductors arranged in slots
H02K 3/48 - Fastening of windings on the stator or rotor structure in slots
H02K 11/25 - Devices for sensing temperature, or actuated thereby
H02K 15/085 - Forming windings by laying conductors into or around core parts by laying conductors into slotted stators
H02K 15/108 - Insulating between conductors and cores with slot liners
37.
FUEL CELL COOLING AND WASTE HEAT RECOVERY SYSTEM FOR GENERATING POWER FOR AIRCRAFT SYSTEMS
A system that provides a cooling liquid to a component of an aircraft, the system having: a cooling circuit that includes a fuel cell that receives a first flow and transfers first waste heat to the first flow; an air cycle machine (ACM) that transfers second waste heat to a second flow; a first heat exchanger, fluidly coupled to the cooling circuit downstream of the fuel cell, that thermally couples the first and second flows to superheat the first flow; a turbine, fluidly coupled to the cooling circuit downstream of the first heat exchanger, that extracts energy from the first flow; and a condenser, fluidly coupled to the cooling circuit downstream of the turbine, that condenses the first flow into the cooling liquid, wherein the component is fluidly coupled to the circuit downstream of the condenser.
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
H01M 8/04007 - Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids related to heat exchange
H01M 8/04119 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants with simultaneous supply or evacuation of electrolyteHumidifying or dehumidifying
A fuel system for an aircraft includes a main fuel pump, a metering valve fluidly connected to the main fuel pump, a selector valve fluidly connected to the metering valve, a check valve fluidly connected to the metering valve, and an electric motor driven start pump fluidly connected to the check valve and the selector valve. During a start-up condition, the fuel system is configured to permit a fuel to flow through the electric motor driven start pump and through the selector valve to an engine. During a cruise condition, the fuel system is configured to permit the fuel to flow from a high-pressure fuel source and through the electric motor driven start pump start pump to drive the electric motor driven start pump to generate electrical energy.
A cooling system includes a fuel supply system and a cooling fuel path. The fuel supply system includes a boost stage pump and a main stage pump, while the cooling fuel path includes a fuel bleed from an outlet of the boost stage pump, a fuel return to an inlet of the boost stage pump, and a cooler disposed fluidly between the fuel bleed and the fuel return.
Apparatus and associated methods relate to a bond-degradation device for testing EMI susceptibility and/or emission suppression of an electrical control system that includes a shielded cable assembly. The bond-degradation device includes a resistive annulus configured to be interposed between normally-connected first and second shielded connectors of the electrical control system. The resistive annulus introduces a resistance between shields of the normally-connected first and second shielded connectors, thereby compromising integrity of the shielding of conductive wires within the shielding of the shielded cable assembly by increasing loop resistance of the shielding.
H05K 9/00 - Screening of apparatus or components against electric or magnetic fields
G01R 31/00 - Arrangements for testing electric propertiesArrangements for locating electric faultsArrangements for electrical testing characterised by what is being tested not provided for elsewhere
H01R 13/6592 - Specific features or arrangements of connection of shield to conductive members the conductive member being a shielded cable
An air cycle machine (ACM) is provided and includes a rotor. The rotor includes a rotor hub, an outlet housing and one or more bearings. The rotor hub includes rear and forward faces, a central portion axially interposed between the rear and forward faces and blades extending radially outwardly from the central portion. The rotor hub defines a pocket having an open end and forms a foil bearing shaft. The outlet housing includes a bearing support element, which is receivable in the pocket via the open end. The one or more bearings are supportively disposed within the bearing support element to support rotation of the foil bearing shaft
An air cycle machine (ACM) is provided and includes a rotor including rear and forward faces and a central portion interposed between the rear and forward faces with outwardly extending blades. The rotor defines a pocket having an open end and forms a foil bearing shaft. The ACM further includes an inlet housing partially surrounding the rotor, an outlet housing including a forward face and a bearing support element extending from the forward face and being receivable in the pocket via the open end, one or more first bearings disposed within the bearing support element to support rotation of the foil bearing shaft, a second bearing interposed between the forward face of the outlet housing and the rear face of the rotor and a third bearing interposed between the forward face of the rotor and the inlet housing.
A planetary gear carrier assembly includes a plurality of planetary gears each rotatable about a respective planet axis defined by a respective pin through the gear, and a planetary gear carrier defining an annular housing having a front face and a back face defining a housing therebetween and an annulus axis. The planetary gears are located within and spaced circumferentially around the housing. A position balancing arrangement is provided for at least one of the plurality of planetary gears, including a slot formed in the front face and back face, extending circumferentially, to receive the pin of the respective at least one of the planetary gears for circumferential movement within the slot, and a resilient element in biased engagement with the pin to adjust the position of the pin in the slot towards a desired position responsive to movement of the pin away from the desired position in the slot.
A pneumatic start system includes a compressor system and an air turbine starter (ATS) comprising an integrated electric generator. Bleed air from the compressor system flows to the air turbine starter, exciting the integrated generator. The ATS regulates a pressure of the bleed air from the compressor system via the integrated generator. The ATS is fluidly coupled to an environmental control system (ECS) bleed system. A fluid connection between the ECS bleed system and the ATS is regulated by a starter air valve (SAV). A second connection between the ECS bleed system and the ATS is regulated by an ECS shut off valve. Pressure regulated fluid flow from the compressor system is delivered to the ECS bleed system via the second fluid connection or is delivered to ambient atmosphere, via a valve fluidly connected between the ATS and the ambient atmosphere, based upon operation of the ECS shut off valve.
F02C 7/277 - Mechanical drives the starter being a turbine
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
45.
ENVIRONMENTAL CONTROL SYSTEM OF AN AIRCRAFT CONFIGURED WITH A TWO-PHASE TURBINE ENCASED WITH A COMPRESSOR AND COUPLED TO A MOTOR HAVING A SHAFT COUPLING
An environmental control system of an aircraft, having: a cooling circuit including: a sealed housing; a turbo-compressor sealed within the housing, wherein the turbo-compressor includes: a compressor fluidly coupled to the circuit; a turbine fluidly coupled to the circuit downstream of the compressor, wherein the turbine is a flash turbine; a shaft operably coupling the compressor and the turbine; a motor generator operably coupled to the turbo-compressor; and an exterior shaft, located exterior to the housing and operably coupled to the motor generator, wherein: the motor generator is within the housing, directly coupled to the turbo-compressor and coupled to the exterior shaft via a coupling, wherein the coupling is one of: a magnetic coupling; a mechanical coupling; a geared axial flux motor; an electro-magnetic geared coupling; or a radial-axial flux permanent magnet (RADAX) motor.
A single shaft, one piece rotor having: a hub that extends from a hub aft end to a hub forward end, wherein the hub aft end defines a first diameter and the hub forward end defines a second diameter that is smaller than the first diameter; a plurality of blade stages extending from a forward end to an aft end, wherein the blade stages are stacked, one on top of the other, radially outwardly from the hub, including an inner stage that is integral with the hub and an outer stage that is radially spaced apart from the hub; and a shroud between adjacent ones of the blade stages.
A system is provided including an ionizer configured to produce and emit charged air ions into an ionization region. The system includes an ion cell configured to output a first voltage corresponding to an ion density associated with the ionization region. The system includes a signal conditioning circuit configured to output a second voltage to the ionizer based on the first voltage. The ionizer is configured to maintain or adjust a setting associated with producing and emitting the charged air ions into the ionization region, based on the second voltage.
B01D 53/32 - Separation of gases or vapoursRecovering vapours of volatile solvents from gasesChemical or biological purification of waste gases, e.g. engine exhaust gases, smoke, fumes, flue gases or aerosols by electrical effects other than those provided for in group
H01T 23/00 - Apparatus for generating ions to be introduced into non-enclosed gases, e.g. into the atmosphere
A planetary gear carrier assembly includes a plurality of planetary gears each rotatable about a respective planet axis defined by a respective pin through the gear, and a planetary gear carrier defining an annular housing having a front face and a back face defining a housing therebetween and an annulus axis. The plurality of planetary gears are located within and spaced circumferentially around the housing, the pin of each planetary gear passing from the front face to the back face at a location such that the planetary gear partially extends radially outwards of the carrier periphery. The carrier is provided with compliance, the compliance provided by one or more portions of reduced stiffness in the front and back faces adjacent the location of the pin of one or more of the planetary gears.
A real-time artificial intelligence and/or machine learning (AI/ML) system for an aircraft can include an AI/ML module configured to receive one or more inputs and to calculate an AI/ML control output. The AI/ML module can include a non-deterministic model for processing the inputs and outputting the AI/ML control output. The system can include a deterministic module configured to receive one or more inputs and the AI/ML control output from the AI/ML module. The deterministic module can include a deterministic model for processing the inputs and/or AI/ML control output to calculate a deterministic condition. The deterministic module can be configured to check the AI/ML control output against the deterministic condition to determine whether to output the AI/ML control output.
A turbine engine for an aircraft includes a compressor with a low-pressure spool including a low-pressure tap and a high-pressure spool including a high-pressure tap and a combustor connected to the compressor. The engine includes a turbine connected to the combustor and that includes an inlet section connected to the outlet portion of the combustor and an outlet section. The engine also includes an integrated engine bleed system connected to the compressor and a plurality of aircraft sub-systems. The integrated engine bleed system connects the high/low pressure taps various aircraft sub-systems.
F02C 9/18 - Control of working fluid flow by bleeding, by-passing or acting on variable working fluid interconnections between turbines or compressors or their stages
51.
Ram air fan including additively manufactured heat exchanger insert
A ram air journal bearing shaft includes an additively manufactured body having a main body portion and a journal bearing portion. The main body portion and the journal bearing portion are coaxial along a first axis. At least a first set of heat exchanger fins extends from an outer diameter of the ram air journal bearing shaft to an inner diameter tie rod passage. Each heat exchanger fin in the first set of heat exchanger fins is additively manufactured as an integral structure to the additively manufactured body. A set of cooling air passages is disposed circumferentially about the first axis. Each cooling air passage is defined between adjacent heat exchanger fins of the first set of heat exchanger fins. The ram air journal bearing shaft is configured such that a cooling flowpath through the cooling air passages is established.
A system with active pressure control includes a sensor, a valve, and a controller. The sensor interfaces with and senses a pressure within a cavity of system component. The valve is disposed along a gas discharge path in fluid communication with a gas outlet port of a separator. The controller varies open area of the valve based on the pressure measured by the sensor.
A system for accelerating a pump includes a fuel source, a pump, a drive, a turbine, and a combustor. The pump has an inlet in fluid communication with the fuel source and an outlet. The drive is rotationally coupled to the pump and configured to drive the pump to thereby pump fuel from the inlet to the outlet of the pump. The turbine rotationally coupled to the drive and the pump. The combustor fluidly communicates with the outlet of the pump and the inlet of the turbine.
A component for use in an environmental control system includes an inlet portion having a longitudinal axis, an inlet formed at the inlet portion, and an outlet portion including a front side and a back side. The front side is arranged closer to the inlet portion than the back side. An outlet is formed at the outlet portion and is arranged at a non-parallel angle relative to the inlet. An intermediate portion extends between and fluidly couples the inlet portion and the outlet portion. The intermediate portion includes a reservoir spaced laterally from the back side of the outlet portion and offset from the longitudinal axis of the inlet portion.
An additively manufactured heat exchanger is provided and includes first and second inlet headers which are interlaced with one another, first and second outlet headers which are interlaced with one another and a core. The core is interposed between a pair of the first and second inlet headers and a pair of the first and second outlet headers. The core includes first pathways by which a first fluid flows from the first inlet header to the first outlet header and second pathways disposed in thermal communication with the first pathways and by which a second fluid flows from the second inlet header to the second outlet header.
F28D 7/00 - Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
F28F 7/02 - Blocks traversed by passages for heat-exchange media
A method includes receiving a callback routine creation command at a target device. The method also includes creating a callback routine in a callback memory space included in memory of the target device after validating the same. The method also includes receiving a set breakpoint command at the target device. The method also includes, in response to the received set breakpoint command, setting a breakpoint at the target device. The method can also include identifying a breakpoint hit, generating, by an exception inducing instruction, an interrupt, identifying a breakpoint control block in an active breakpoints data structure. The method also can also include invoking the callback routine and storing an opcode at a memory address, wherein the memory address is in a predetermined memory region of the memory, and wherein the breakpoint control block stores the opcode and the memory address.
A voltage converter for converting an input voltage to an output voltage includes a controller arranged to: superpose a power line communication signal onto a target DC output voltage to provide a target output voltage; compare the output voltage of the voltage converter with the target output voltage; and adjust operation of the voltage converter so as to drive the output voltage towards the target output voltage.
H02M 3/335 - Conversion of DC power input into DC power output with intermediate conversion into AC by static converters using discharge tubes with control electrode or semiconductor devices with control electrode to produce the intermediate AC using devices of a triode or a transistor type requiring continuous application of a control signal using semiconductor devices only
H02M 3/00 - Conversion of DC power input into DC power output
H04B 3/54 - Systems for transmission via power distribution lines
58.
Fuel system with boosted and cooled variable displacement main fuel pump and electromechanical actuators
A fluid system includes a boost pump and a variable displacement pump along a main leg configured to output fluid within a pressure range and at variable flow rates. An auxiliary leg of the fluid system includes an auxiliary pump configured to receive a portion of the fluid from the main leg and to output pressurized fluid to a control valve of the variable displacement pump and multiple actuator modules. Each actuator module includes an electromechanical actuator and a collocated control unit.
A stratospheric capsule includes: a capsule interior configured to enclose occupants during a stratospheric space flight; a capsule exterior; and an environmental control system (ECS) configured to control one or more of temperature and humidity in the capsule interior during the stratospheric space flight. The ECS includes: an internal air-cooling heat exchanger that cools air within the capsule by passing air across a cooling fluid within the ECS and a phase change material (PCM) heat exchange assembly located within the capsule interior. First and second valves are arranged and configured to be controlled based on the temperature measured by the temperature sensor measuring air passing through the internal air-cooling heat.
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
60.
BASE-TO-EMITTER VOLTAGE TEMPERATURE COMPENSATION FOR TRANSISTOR INCLUDED IN SENSOR EXCITATION CIRCUIT
A sensor excitation circuit includes a voltage driver circuit and a short-circuit protection circuit. The voltage driver circuit selectively conducts electrical current via a driver output in response to a first operating voltage exceeding a driver voltage threshold (V1be). The short-circuit protection circuit includes a protection semiconductor switching device and a temperature compensation circuit. The protection semiconductor switching device limits the electrical current through the voltage driver circuit in response to switching on when a second operating voltage exceeds a protection voltage threshold (V2be). The temperature compensation circuit is connected to the protection semiconductor switching device, and is configured to limit a variation of the protection threshold voltage (V2be) in response to exposing the protection semiconductor switching device to different temperatures.
H03K 17/0814 - Modifications for protecting switching circuit against overcurrent or overvoltage without feedback from the output circuit to the control circuit by measures taken in the output circuit
H03K 17/14 - Modifications for compensating variations of physical values, e.g. of temperature
H03K 17/60 - Electronic switching or gating, i.e. not by contact-making and -breaking characterised by the use of specified components by the use, as active elements, of semiconductor devices the devices being bipolar transistors
61.
ENVIRONMENTAL CONTROL SYSTEM WITH MIXED BLEED AND AMBIENT PACK
An air conditioning system of a vehicle includes a plurality of inlets operable to receive a plurality of mediums. The plurality of inlets include a first inlet operable to receive a first medium and a second inlet operable to receive a second medium. The air conditioning system additionally include an outlet and a thermodynamic device operably coupled to the plurality of inlets and to the outlet. The thermodynamic device includes a compressor, a first turbine, and a second turbine, operably coupled by a shaft. The second turbine includes a plurality of flow paths. The plurality of flow paths of the second turbine are fluidly coupled to an upstream component in parallel relative to a flow of the first medium.
A system is provided including a pulse width modulation controller configured to control a first output voltage of a first power supply associated with the system, wherein the first power supply is referenced to an input ground associated with the system. The system includes a programmable device configured to control at least a second output voltage of a second power supply associated with the system, wherein the second power supply is referenced to an output ground associated with the system. The programmable device is powered based on the first output voltage.
H02M 1/08 - Circuits specially adapted for the generation of control voltages for semiconductor devices incorporated in static converters
H02M 1/32 - Means for protecting converters other than by automatic disconnection
H02M 3/335 - Conversion of DC power input into DC power output with intermediate conversion into AC by static converters using discharge tubes with control electrode or semiconductor devices with control electrode to produce the intermediate AC using devices of a triode or a transistor type requiring continuous application of a control signal using semiconductor devices only
63.
EMI EMISSION CONTROL ON LOW POWER SUPPLIES IN A MOTOR DRIVE APPLICATION
A system is provided including a pulse width modulation controller configured to control a first output voltage of a first power supply associated with the system, wherein an input to the first power supply is referenced to an input ground associated with the system and the first output voltage is referenced to a first output ground associated with the system. The system includes a programmable device configured to control a second output voltage of a second power supply associated with the system, wherein an input to the second power supply is referenced to the input ground associated with the system and the second output voltage is referenced to a second output ground associated with the system. The programmable device is powered based on the first output voltage.
H02P 7/29 - Arrangements for regulating or controlling the speed or torque of electric DC motors for regulating or controlling an individual DC dynamo-electric motor by varying field or armature current by master control with auxiliary power using discharge tubes or semiconductor devices using semiconductor devices controlling armature supply only using pulse modulation
64.
EMI EMISSION CONTROL ON DC-DC CONVERTERS IN A MOTOR DRIVE APPLICATION WITH MULTIPLE ISOLATED INPUT VOLTAGES AND OUTPUT VOLTAGES
A system includes a pulse width modulation controller configured to control a first output voltage of a first power supply associated with the system. The first power supply is referenced to a first input ground associated with the system and the first output voltage is referenced to a first output ground associated with the system. The system includes a programmable device configured to configured to control a second output voltage of a second power supply associated with the system. The second power supply is referenced to a second output ground associated with the system. The programmable device is powered based on the first output voltage.
H02M 1/08 - Circuits specially adapted for the generation of control voltages for semiconductor devices incorporated in static converters
H02M 1/32 - Means for protecting converters other than by automatic disconnection
H02M 3/335 - Conversion of DC power input into DC power output with intermediate conversion into AC by static converters using discharge tubes with control electrode or semiconductor devices with control electrode to produce the intermediate AC using devices of a triode or a transistor type requiring continuous application of a control signal using semiconductor devices only
An electrical power-transfer system for an engine includes first and second engine shafts. The system also includes a planetary gear system having a sun gear, a ring gear, a plurality of planetary gears enmeshed with the sun gear and the ring gear, and a carrier supporting the plurality of planetary gears, where the carrier is configured for connection to be driven by the first engine shaft. The system further includes a first electrical machine connected to be driven by the ring gear to generate electrical power, a second electrical machine connected to drive the sun gear, and a third electrical machine configured to receive electrical power generated by the first electrical machine and operable as a motor to drive the second engine shaft.
A direct current (DC) voltage monitoring circuit includes a switch mode power supply, a transformer, and a rectifier circuit. The switch mode power supply provides an input voltage. The transformer includes a primary winding in signal communication with the switch mode power supply. The transformer stores energy induced by a primary voltage applied across the transformer by the input voltage (Vin) in response to the switch mode power supply operating in the “ON” state, releases the energy as a secondary voltage to be used as an output voltage in response to the switch mode power supply operating in the “OFF” state. The rectifier circuit generates a monitored voltage indicative of the input voltage in response to the switch mode power supply operating in the “ON” state, and rectifies the output voltage generated by the transformer in response to the switch mode power supply operating in the “OFF” state.
G01R 19/00 - Arrangements for measuring currents or voltages or for indicating presence or sign thereof
H02M 3/335 - Conversion of DC power input into DC power output with intermediate conversion into AC by static converters using discharge tubes with control electrode or semiconductor devices with control electrode to produce the intermediate AC using devices of a triode or a transistor type requiring continuous application of a control signal using semiconductor devices only
A synchronous machine includes a first set of windings, including a first winding and n−1 other windings. The synchronous machine also includes a second set of windings, including a first winding and n−1 other windings. The synchronous machine further includes first inverter circuitry electrically coupled to a second end of each of the n−1 other windings of the first set, a first switch electrically coupled between the first inverter circuitry and a second end of the first winding of the first set, second inverter circuitry electrically coupled to a second end of each of the n−1 other windings of the second set, and a second switch electrically coupled between the second inverter circuitry and a second end of the first winding of the second set. In addition, the synchronous machine includes a third switch electrically coupled between the second ends of the first windings and control circuitry configured to switch the machine between parallel and series configurations.
H02P 25/18 - Arrangements or methods for the control of AC motors characterised by the kind of AC motor or by structural details characterised by the circuit arrangement or by the kind of wiring with arrangements for switching the windings, e.g. with mechanical switches or relays
H02P 25/22 - Multiple windingsWindings for more than three phases
68.
ENVIRONMENTAL CONTROL SYSTEM USING ARCHITECTURE WITH TURBINES IN SERIES AND A MID-PRESSURE WATER SEPARATOR
An environmental control system of a vehicle includes a first inlet for receiving a first medium, a second inlet for receiving a second medium, a thermodynamic device operably coupled to the first inlet and the second inlet, and an expansion device operably coupled to the second inlet. The thermodynamic device includes a compressor and a plurality of turbines operably coupled by a shaft. The expansion device is independently operable from the thermodynamic device. The first inlet is fluidly coupled to a turbine of the plurality of turbines via a first flow path and the second inlet is fluidly connected to another turbine of the plurality of turbines via a second flow path. In at least one mode, the first medium is provided to the turbine and the another turbine in parallel.
An environmental control system of a vehicle includes an air conditioning system having a first inlet configured to receive a first medium and a second inlet configured to receive a second medium. An air supply system including a thermodynamic device is fluidly coupled to the air conditioning system. The thermodynamic device includes a compressor operably coupled to an electric motor and a turbine by a shaft. T the thermodynamic device is fluidly coupled to and is arranged upstream from the first inlet relative to a flow of the first medium and the thermodynamic device is fluidly coupled to and is arranged downstream from the second inlet relative to a flow of the second medium. The electric motor is fluidly coupled to an inlet of the turbine and the turbine is arranged directly downstream from the electric motor relative to the flow of the second medium.
B64D 13/02 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being pressurised
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
70.
CHECK VALVE FOR RAM AIR TURBINE (RAT) RE-STOW PUMP
A check valve assembly includes a valve body having first and second ends, a check valve outlet between the ends, and an actuator port axially between the check valve outlet and the second end. The valve body includes a fluid inlet axially between the actuator port and the second end. The check valve assembly also includes check valve components configured to control fluid flow entering and leaving the valve body. The check valve components include first and second spools, a first check valve spring in spring force engagement with the first spool, and a second check valve spring in spring force engagement with the second spool. The first check valve spring biases the first spool into seating engagement with a valve seat. The second check valve spring biases the second spool towards the second end. Each valve spool moves out of seating engagement in response to a predetermined differential pressure.
A voltage regulator is provided including a pulse width modulation controller configured to control an output voltage of a power supply and a programmable device configured to monitor the output voltage of the power supply. The programmable device is configured to assume control of the output voltage of the power supply based on a comparison by the programmable device of the output voltage of the power supply to one or more criteria. The programmable device assumes control of the output voltage by producing a replica of the output signal provided by the pulse width modulation controller, which is fed from the secondary side to the primary side of the voltage regulator.
H02M 3/335 - Conversion of DC power input into DC power output with intermediate conversion into AC by static converters using discharge tubes with control electrode or semiconductor devices with control electrode to produce the intermediate AC using devices of a triode or a transistor type requiring continuous application of a control signal using semiconductor devices only
G06F 1/26 - Power supply means, e.g. regulation thereof
An electro-mechanical actuator architecture is provided for a cowl door of an aircraft engine nacelle. The electro-mechanical actuator architecture includes a screw shaft, a drive disc connected to the screw shaft, a clutch disposed on a first side of the drive disc, the clutch including a first friction disc with a first skew angle, and a no-back unit disposed on a second side of the drive disc, which is opposite the first side, the no-back unit including a second friction disc with a second skew angle, the first skew angle being higher than the second skew angle.
A system for transpiration cooling of an outer surface of an aircraft, the system having: a flow conditioning circuit that has: an upstream end defining a RAM airflow inlet that receives a RAM airflow, and a first injection port near the upstream end, through which a first flow of liquid nitrogen is injected into the flow conditioning circuit; a first turbine, coupled to the flow conditioning circuit, downstream of the first injection port, that receives the RAM airflow, extracts energy from the RAM airflow, and directs the RAM airflow downstream along the flow conditioning circuit; and wherein the flow conditioning circuit directs the RAM airflow downstream from the first turbine to the outer surface of the aircraft.
An environmental control system of a vehicle includes a first inlet for receiving a first medium, a second inlet for receiving a second medium, an outlet. The outlet is only fluidly connected to the second inlet. A ram air circuit including at least one ram heat exchanger is fluidly connected to at least one of the first inlet and the second inlet. A thermodynamic device includes a compressor and a plurality of turbines operably coupled by a shaft. The thermodynamic device is fluidly coupled to both the first inlet and the second inlet. A first cooling medium is provided to the ram air circuit during a first mode of operation, and a second cooling medium is provided to the ram air circuit during a second mode of operation.
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
75.
BLEEDLESS ENVIRONMENTAL CONTROL SYSTEM WITH MOTORIZED AIR CYCLE MACHINE
An environmental control system of a vehicle includes a first inlet for receiving a first medium, a second inlet for receiving a second medium, and at least one thermodynamic device fluidly coupled to the first inlet and the second inlet. The at least one thermodynamic device includes a compressor, at least one turbine, and an electric motor, operably coupled by a shaft. The second inlet is fluidly connected to the electric motor such that a flow of the second medium is operable as a heat sink to remove heat from the electric motor.
B64D 13/02 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being pressurised
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
An environmental control system of a vehicle includes an air conditioning system having a first inlet for a first medium, a second inlet for a second medium, and a first thermodynamic device including a first compressor, a first electric motor and a first turbine operably coupled by a first shaft. An air supply system includes a second thermodynamic device fluidly coupled to the air conditioning system. The second thermodynamic device includes a second compressor operably coupled to a second electric motor by a second shaft. The second thermodynamic device is fluidly coupled to and is arranged upstream from the first inlet relative to a flow of the first medium and is fluidly coupled to and is arranged downstream from the second inlet relative to a flow of the second medium. The second electric motor is fluidly coupled to and is cooled by the second medium provided at the second inlet.
F24F 11/86 - Control systems characterised by their outputsConstructional details thereof for controlling the temperature of the supplied air by controlling compressors within refrigeration or heat pump circuits
77.
Compact single variable displacement pump fuel system with high pressure fuel oil cooler bypass and gas generator fault
A fuel system for a gas turbine engine includes a fuel control with an outlet for connection to a burner. The fuel system includes a first pump unit connected to a gear box. The first pump unit includes a first housing, a first drive shaft connected to the gearbox, and a main pump within the first housing and powered by the first drive shaft. A stability-shutoff valve is in the first housing and includes an inlet connected to an outlet of the main pump. A fuel-oil-cooler bypass valve is in the first housing and includes an inlet connected to an outlet of the stability-shutoff valve and an outlet connected to an inlet of the fuel control. The fuel system also includes a fuel oil cooler with a fuel inlet connected to the outlet of the stability-shutoff valve and a fuel outlet connected to the inlet of the fuel control.
Baffle assemblies for use with condensing heat exchangers include a housing with a portion of the housing having a water flow passage defined therein, a set of baffles extending from the housing and arranged with a fluid connection with the water flow passage. Each baffle of the set of baffles includes a baffle frame having a solid back and solid sidewalls that define an open faced baffle cavity, a primary layer arranged within the baffle cavity, wherein the primary layer comprises a geometry pattern of openings, and a secondary layer arranged within the baffle cavity between the primary layer and the back of the baffle frame, with the secondary layer being formed of a mesh of woven wires.
F24F 13/22 - Means for preventing condensation or evacuating condensate
B64G 1/48 - Arrangements or adaptations of devices for control of environment or living conditions for treatment of the atmosphere
F24F 3/14 - Air-conditioning systems in which conditioned primary air is supplied from one or more central stations to distributing units in the rooms or spaces where it may receive secondary treatmentApparatus specially designed for such systems characterised by the treatment of the air otherwise than by heating and cooling by humidificationAir-conditioning systems in which conditioned primary air is supplied from one or more central stations to distributing units in the rooms or spaces where it may receive secondary treatmentApparatus specially designed for such systems characterised by the treatment of the air otherwise than by heating and cooling by dehumidification
79.
FUEL SYSTEM WITH FUEL COOLED ELECTRIC GENERATION AND FUEL OIL COOLER ELIMINATION
An aircraft fuel system includes a fuel tank, a fuel pump configured to receive a fuel flow from the fuel tank via a fuel supply line. The fuel system further includes a tap fluidly coupled to an outlet of the fuel pump, at least one generator or permanent magnet machine fluidly connected to the fuel pump via the tap, and the tap is configured to deliver fuel to the at least one generator or permanent magnet machine. The fuel system further includes a gearbox mechanically connected to the at least one generator or permanent magnet machine.
An aircraft fuel system includes a first integrated boost stage having a boost pump configured to receive a fuel flow from a fuel tank via a boost supply line, at least one generator collocated with and operatively connected to the boost pump for driving the boost pump, and a tap fluidly connecting the boost pump and the at least one generator for selectively delivering an amount of the fuel flow to the at least one generator. The fuel system further includes a gearbox operatively connected to the at least one generator, and a main stage downstream of the boost stage and operatively connected to the gearbox. The main stage includes a main pump configured to receive the fuel flow from the boost pump along a main supply line, and a filter disposed along the main supply line upstream of the main pump for filtering the fuel flow.
A planar transformer includes a stack comprising a plurality of planar windings arranged one above the other, an outer core portion comprising a first plate and a second plate, an inner core portion extending between the first plate and the second plate, and at least one heat pipe. The planar windings are disposed between the first plate and the second plate. Each planar winding of the plurality of planar windings, the first plate and the second plate extend substantially parallel to each other. The at least one heat pipe extends substantially parallel to the plurality of planar windings and is disposed in a space formed between a planar winding of the plurality of planar windings and any of: another planar winding of the plurality of planar windings, the first plate, or the second plate.
A synchronous rectifier including a first rectifier current path. The first rectifier current path has a first and second switching arrangement, which are arranged in series. The first switching arrangement includes a first switch and the second switching arrangement includes a second switch. A first current sensor is arranged to measure a current through the first rectifier current path; and a controller is arranged to operate the first switch and the second switch based on the current measured by the first current sensor.
H02M 7/217 - Conversion of AC power input into DC power output without possibility of reversal by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only
H02M 1/08 - Circuits specially adapted for the generation of control voltages for semiconductor devices incorporated in static converters
H02M 3/00 - Conversion of DC power input into DC power output
H02M 3/335 - Conversion of DC power input into DC power output with intermediate conversion into AC by static converters using discharge tubes with control electrode or semiconductor devices with control electrode to produce the intermediate AC using devices of a triode or a transistor type requiring continuous application of a control signal using semiconductor devices only
A drive system for operating a ram air turbine (RAT) re-stow pump assembly includes a pump piston and a cylinder in which the pump piston moves axially in a reciprocating linear motion when driven by the drive system. The drive system includes a rotary drive shaft and a linear link member having a first end connected to the rotary drive shaft and a second end arranged to be connected, in use, to the pump piston of the RAT re-stow pump. Rotation of the drive shaft is translated to reciprocal linear motion of the piston when connected to the link member, via the link member. The drive shaft is provided with an attachment fitting configured to attach to a rotary power tool, in use, to drive rotation of the drive shaft.
A system for identifying series arcing in an electrical distribution network of an aircraft includes a plurality of local sensors, a plurality of local processors, and a global processor. Each local sensor measures a measurement representative of the voltage, current and/or impedance in a component of the electrical distribution network. Each local processor analyzes the measurement measured by the respective local sensor and outputs a signal representative of the complexity of the measurement. The global processor receives the signals from the plurality of local processors, analyzes the signals, and determines when series arcing is occurring in the electrical distribution network. The global processor outputs a signal indicative of the series arcing in the electrical distribution network when it has been determined that series arcing is occurring.
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
G01R 31/00 - Arrangements for testing electric propertiesArrangements for locating electric faultsArrangements for electrical testing characterised by what is being tested not provided for elsewhere
G01R 31/12 - Testing dielectric strength or breakdown voltage
A part including corrosion- and wear-resistant regions has a base alloy with a plurality of surfaces, a corrosion-resistant coating deposited on at least one surface, and a wear-resistant coating deposited on at least one surface. The corrosion-resistant coating includes a thin film sulfuric acid anodize sealed with sequentially applied dipotassium hexafluorozirconate, lanthanum nitrate hexahydrate plus hydrogen peroxide, and hydrothermal seal systems. The wear-resistant coating comprises hardcoat anodize.
An axial variable displacement piston pump includes a drive shaft disposed on an axis, a piston barrel having a plurality of pistons disposed about and rotationally coupled to the drive shaft, a swash plate disposed about and rotationally coupled to the drive shaft, and a retention cage connected to the swash plate between the piston barrel and the swash plate. The swash plate and the piston barrel are configured to be simultaneously driven by the drive shaft and the swash plate is configured to tilt relative to the axis. The retention cage is configured to retain the plurality of pistons relative to the swash plate with rotation.
F04B 1/324 - Control of machines or pumps with rotary cylinder blocks by varying the relative positions of a swash plate and a cylinder block by changing the inclination of the swash plate
A ram air journal bearing shaft includes an additively manufactured body having a main body portion and a journal bearing portion. The main body portion and the journal bearing portion are coaxial along a first axis. The additively manufactured body includes at least a first set of regions additively manufactured using a first material and a second set of regions additively manufactured using a second material. At least a first set of heat exchanger fins extends from an outer diameter of the ram air journal bearing shaft to an inner diameter tie rod passage. Each heat exchanger fin in the first set of heat exchanger fins is additively manufactured as an integral structure to the additively manufactured body. A set of cooling air passages are disposed circumferentially about the first axis. Each cooling air passage is defined between adjacent heat exchanger fins of the first set of heat exchanger fins and the ram air journal bearing shaft is configured such that a cooling flowpath through the cooling air passages is established.
A thermal management system for high-flow venting of a battery pack which includes the battery pack, a vent chamber, a pressure release mechanism (V1), an inlet valve (V2) and an outflow pressure release system (V3, V4). The pressure release mechanism is configured to either block a flow or relieve the burst pressure from the battery pack to the vent chamber, when the pressure in the battery pack is less than, or greater than, a burst pressure respectively. The outflow pressure release system is configured to either permit an outflow of gas at up to a first flow rate, or at greater than a second flow rate, from the vent chamber to the external environment, when the pressure in the vent chamber is less than, or alternatively greater than, a release pressure respectively. The second flow rate is greater than the first flow rate.
A speed signal converter circuit including an analog signal conditioning stage and a digital signal processing stage. The analog signal conditioning stage determines a voltage of an input speed signal, combines the voltage with an alternating current (AC) injection voltage signal having a set frequency to generate a combined voltage signal, and outputs a pulsed zero-crossing signal including a rising edge and a falling edge indicating a zero-crossing of the input speed signal based on the combined voltage signal. The digital signal processing stage determines a rising edge slope of the input speed signal and a falling edge slope of the input signal based on a rising edge and a falling edge of the pulsed zero-crossing signal, and determines an optimal edge among one of the rising edges or the falling edges based on a comparison between the rising edge slope and the falling edge slope.
G01P 3/481 - Devices characterised by the use of electric or magnetic means for measuring angular speed by measuring frequency of generated current or voltage of pulse signals
G01P 21/02 - Testing or calibrating of apparatus or devices covered by the other groups of this subclass of speedometers
90.
ENHANCED METHOD TO TROUBLESHOOT AIRCRAFT ELECTRIC POWER GENERATING SYSTEM FAULT EVENTS
A fault analysis system, including: a memory device including a circular buffer, and one or more processors configured to continuously capture status signals associated with an electric power generating system of an aircraft and store the status signals to the circular buffer. The one or more processors are configured to, in response to detecting a fault event associated with the electric power generating system, store pre-fault snapshot data and fault snapshot data associated with the fault event to the memory device. The pre-fault snapshot data includes a first portion of the stored status signals corresponding to a temporal period prior to a time point associated with occurrence of the fault event. The fault snapshot data includes a second portion of the stored status signals corresponding to the time point associated with occurrence of the fault event.
A method for providing a wear-resistant component includes depositing an aluminum coating on a steel component to provide an aluminum-coated steel component, and subjecting the aluminum-coated steel component to a plasma electrolytic oxidation (PEO) process. The PEO process converts a surface portion of the aluminum coating to alumina. A wear-resistant component includes a steel component and a wear-resistant coating on the steel component. The wear-resistant coating includes an alumina surface portion and an underlying portion of either aluminum or aluminum and nickel combination or nickel aluminide that contacts the steel component.
C23C 28/00 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and
An environmental control system of a vehicle includes a first inlet for providing a first medium, a second inlet for providing a second medium. The second medium is different than the first medium. A thermodynamic device is fluidly connected to the first and second inlets. The thermodynamic device includes a compressor and at least one turbine operably coupled by a shaft. The environmental control system is operable in a plurality of modes, and in a first mode of the plurality of modes, the thermodynamic device is driven solely by energy extracted from the first medium.
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
F02C 6/08 - Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
93.
METHOD TO PROMOTE AIRCRAFT ELECTRIC POWER GENERATING SYSTEM FAULTS FROM LOWER SEVERITY TO HIGHER SEVERITY BASED ON FREQUENCY OF OCCURRENCE
A fault analysis system is disclosed. The fault analysis system includes one or more processors configured to: continuously capture status signals corresponding to a plurality of fault events, wherein the plurality of fault events are associated with an electric power generating system of an aircraft; count a quantity of instances of a fault event of a target severity level with respect to a target quantity of flights, wherein the fault event is included in the plurality of fault events; generate a second fault event associated with the fault event based on comparing the quantity of the instances to a threshold quantity, wherein the second fault event is of a second severity level different from the target severity level; and report the second fault event according to the second severity level.
B64F 5/60 - Testing or inspecting aircraft components or systems
G07C 5/00 - Registering or indicating the working of vehicles
G07C 5/08 - Registering or indicating performance data other than driving, working, idle, or waiting time, with or without registering driving, working, idle, or waiting time
A cooling system for an aircraft capable of travelling at hypersonic speeds includes an inlet configured to receive a first medium and a thermodynamic device fluidly connected to the inlet. The thermodynamic device includes at least one turbine and a compressor operably coupled via a shaft. An outlet of the at least one turbine is directly fluidly connected to an inlet of the compressor. An electric generator is operably coupled to the at least one turbine.
A system comprising: a gas turbine having a combustion chamber and a turbine; a first heat exchanger configured to receive a first stream of compressed air and a stream of liquid hydrogen, wherein the first heat exchanger is configured to transfer heat between the first stream of compressed air and the stream of liquid hydrogen to yield a stream of liquid oxygen and a stream of gaseous hydrogen; a second heat exchanger configured to heat the stream of liquid oxygen to yield a stream of gaseous oxygen; and a third heat exchanger configured to receive a stream of flue gas from the turbine and at least one of the stream of gaseous hydrogen and the stream of gaseous oxygen, wherein the third heat exchanger is configured to transfer heat between the stream of flue gas and the stream of gaseous hydrogen and/or the stream of gaseous oxygen to superheat the stream of hydrogen and/or the stream of oxygen; wherein the system is configured to direct the stream of hydrogen and the stream of oxygen to the combustion chamber, wherein at least one of the stream of hydrogen and the stream of oxygen is superheated.
H01M 8/04007 - Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids related to heat exchange
H01M 8/04111 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants using a compressor turbine assembly
A fuel delivery system for a gas turbine engine includes a fuel source, a main fuel pump configured to deliver a first flow of fuel to a combustor assembly of the gas turbine engine, a main fuel filter positioned upstream of the main fuel pump, and an actuation pump disposed upstream of the main fuel filter and configured to deliver a second flow of fuel from the fuel source to one or more actuation devices of the gas turbine engine.
F02C 7/236 - Fuel delivery systems comprising two or more pumps
F02C 9/28 - Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed
B01D 35/00 - Filtering devices having features not specifically covered by groups , or for applications not specifically covered by groups Auxiliary devices for filtrationFilter housing constructions
An apparatus includes a gearset that includes an input gear configured to be rotated by an input shaft, first and second one-way clutches, first and second output gears configured to drive rotation of an output shaft via the first and second one-way clutches, respectively, and an idler gear. The second output gear has a smaller outer diameter than the first output gear. The input gear is configured to (i) rotate the first output gear in a first direction and (ii) rotate the idler gear in the first direction. The idler gear is configured to rotate the second output gear in a second direction opposite the first direction. The first and second one-way clutches are configured to allow the first and second output gears to drive rotation of the output shaft in a single predetermined rotational direction regardless of a rotational direction of the input shaft.
F16H 1/00 - Toothed gearings for conveying rotary motion
F16H 1/20 - Toothed gearings for conveying rotary motion without gears having orbital motion involving more than two intermeshing members
F16H 1/22 - Toothed gearings for conveying rotary motion without gears having orbital motion involving more than two intermeshing members with a plurality of driving or driven shaftsToothed gearings for conveying rotary motion without gears having orbital motion involving more than two intermeshing members with arrangements for dividing torque between two or more intermediate shafts
H02K 7/116 - Structural association with clutches, brakes, gears, pulleys or mechanical starters with gears
H02K 9/193 - Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil with provision for replenishing the cooling mediumArrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil with means for preventing leakage of the cooling medium
An insulation system, having a plurality of materials forming a composition gradient that defines a first coefficient of thermal expansion (CTE) and a second CTE that differs from the first CTE, wherein the plurality of materials include one or more of different metals, plastics, or fibers, and wherein: at a first temperature the insulation system has a first insulation thickness to provide first heat transfer characteristics; and at a second temperature that is less than the first temperature the insulation system has a second insulation thickness that is greater than the first insulation thickness to provide second heat transfer characteristics that are more insulative than the first heat transfer characteristics.
An environmental-control-system (ECS) for delivering ECS supply air to a cabin having: a first mixer that receives the ECS supply air; a first vapor-cycle-system (VCS) coupled to the first mixer and includes: a first working fluid; a first compressor; a first condenser; a first turbine that is a flash-liquid-expander (FLE) turbine, that receives the first working fluid as a liquid and outputs the first working fluid as a two-phase mixture; a first interconnecting shaft coupling the first compressor and the first turbine; a first evaporator; a second mixer; a bypass connected in parallel with the first VCS, between the first mixer and the second mixer; and in predetermined operational conditions: the first mixer directs the ECS supply air to the second mixer via one or both of the first VCS and the bypass; and the second mixer directs the ECS supply air to the cabin.
A fuel delivery system for a gas turbine engine includes a fuel source, and a main fuel pump configured to deliver a first flow of fuel to a combustor assembly of the gas turbine engine. A fuel oil cooler is positioned fluidly between the main fuel pump and the combustor assembly configured to cool oil utilized by the fuel delivery system, and a fuel oil cooler bypass pathway is configured to selectably direct the first flow of fuel to bypass the fuel oil cooler.
